-
Copyright © ASPEQ Limited 2011 1 of 20
WB-FCL3 Workbook
Subject 032: Flight Performance - Aeroplane
Revision 3
IMPORTANT NOTE This workbook is for use in flight crew
examinations ONLY and is not to be made available for any other
purpose. Not all examinations will require the use of this
workbook, however, when the use of this workbook is required,
candidates will be directed to the appropriate diagram in the text
of the question. You are not permitted to copy or remove any part
of this workbook from the examination room. Once the examination
has been completed, return the workbook to the exam supervisor with
your examination paper. Failure to comply with these instructions
may result in your examination answers not being accepted.
-
2 of 20 Copyright © ASPEQ Limited 2011
DIAGRAM 32.2
Performance Data - Single Reciprocating Engine Aeroplane
(SRE)
General Information This performance data is for a generic small
aeroplane which is configured as follows:
Monoplane Single reciprocating engine Constant speed propeller
Retractable undercarriage Performance Class B Maximum Take-off Mass
2,000kg Maximum Landing Mass 2,000kg Maximum fuel load 300l Fuel
density 0.72 kg/l (unless otherwise stated)
Take-off Performance (SRE) • Class B aeroplane must comply with
both minimum field length and climb gradient requirements. •
Maximum demonstrated crosswind 15kt. Field Length Requirements • If
no stopway or clearway is available the take-off distance must not
exceed 1.25 x TORA. • If no stopway and/or clearway are/is
available the take-off distance must not exceed:
(a) TORA (b) 1.3 x ASDA (c) 1.15 x TODA
• If the runway is not a dry paved surface, then the following
factor must be applied:
(a) Wet paved surface: x 1.0 (b) Dry grass surface: x 1.2 (c)
Wet grass surface: x 1.3
Take-off Speeds The Take-off and Obstacle Clearance Distance
graph is based on the following speeds:
MASS (kg) TAKE-OFF SPEED (kt)
ROTATION 50ft
2,000
1,750
1,500
1,250
74
72
69
67
86
83
80
77
-
Copyright © ASPEQ Limited 2011 3 of 20
DIAGRAM 32.4
Take-Off and Obstacle Clearance Distance (SRE)
-50
0+
50
2,0
00
1,7
50
1,5
00
1,2
50
0-1
010
30
20
050
250
500
750
1,0
00
ISA
10,0
00
8,0
00
6,0
00
4,0
00
2,0
00 SL
PR
ES
SU
RE
ALT
ITU
DE
(ft
)
MA
SS
(kg
)H
EA
DW
IND
(kt)
OB
ST
AC
LE
HE
IGH
T (
ft)
REFERENCE LINE
REFERENCE LINE
REFERENCE LINE
TAKE-OFF DISTANCE (m)
Exam
ple
Tem
pera
ture
= 2
5˚C
Altitude =
2,5
00ft
Take-o
ff m
ass =
1,8
50kg
Headw
ind =
15kt
Take-o
ff r
oll
= 3
90m
Take-o
ff d
ista
nce (
over
50ft o
bsta
cle
) =
530m
TE
MP
ER
AT
UR
E (̊
C)
-
4 of 20 Copyright © ASPEQ Limited 2011
DIAGRAM 32.6
Cruise Power Settings (SRE)
The following table provides cruise power settings, together
with resultant fuel flow and airspeed for a single
reciprocating engine (SRE) aeroplane:
Cruise Power Adjustments
• Reduce/increase fuel flow by 1kg/hr per 10˚C above/below
ISA.
• Reduce/increase IAS and TAS by 3kt per 10˚C above/below
ISA.
Range and Endurance (SRE)
14,000
12,000
10,000
8,000
6,000
4,000
2,000
SL
5:00 7:006:00
ENDURANCE (hrs)
RANGE (nm)
800 850 900
Cruise Power
Full Throttle
Data includes start, taxi,
take-off and 45 minutes
reserve at cruise power.
Example
For cruise at 7,000 feet:
Endurance = 5:20
Range = 838nm
PRESSURE
ALTITUDE (ft)
Pressure
altitude (feet)
IOAT (˚C) Manifold
pressure (“Hg)
Fuel Flow
(kg/hr)
Airspeed
IAS (kt) TAS (kt)
0 17 24.0 29 145 145
2,000 13 24.0 30 145 147
4,000 9 24.0 31 146 152
6,000 5 24.0 33 146 157
8,000 1 23.3 32 144 159
10,000 -3 21.8 30 138 158
12,000 -7 19.6 28 127 150
14,000 -11 17.7 26 118 144
-
Copyright © ASPEQ Limited 2011 5 of 20
DIAGRAM 32.8
Landing Performance (SRE)
-50
0+
50
2,0
00
1,7
50
1,5
00
1,2
50
0-1
010
30
20
050
250
500
750
1,0
00
ISA
10
,00
0
PR
ES
SU
RE
ALT
ITU
DE
(ft
)
MA
SS
(kg
)H
EA
DW
IND
(kt)
OB
ST
AC
LE
HE
IGH
T (
ft)
REFERENCE LINE
REFERENCE LINE
REFERENCE LINE
DISTANCE (m)
Exam
ple
Tem
pera
ture
= 2
2˚C
Altitude =
2,0
00ft
Landin
g m
ass =
1,5
80kg
Headw
ind =
10kt
Landin
g r
oll =
145m
Landin
g d
ista
nce (
over 50ft
obsta
cle
) =
210m
TE
MP
ER
AT
UR
E (
˚C)
8,0
00
6,0
00
4,0
00
2,0
00
SL
-
6 of 20 Copyright © ASPEQ Limited 2011
DIAGRAM 32.10
Performance Data – Light Twin Reciprocating Engine Aeroplane
(LTA) General Information
This performance data is for a generic light twin-engine
aeroplane which is configured as follows:
Monoplane
Two reciprocating engines
Two counter-rotating constant speed propellers
Retractable undercarriage
Performance Class B
Maximum Take-off Mass 2,800kg
Maximum Zero Fuel Mass 2,200kg
Maximum fuel load 350l
Fuel density 0.72 kg/l (unless otherwise stated)
For weights below 2,000kg, use the 2,000kg performance data.
Take-off Performance
• Class B aeroplanes must comply with minimum field length
(take-off and accelerate-stop distance) and climb
gradient requirements.
• Maximum demonstrated crosswind 22kt.
Field Length Requirements
• If no stopway or clearway is available the take-off distance
must not exceed 1.25 x TORA.
• If a stopway and/or clearway are/is available the take-off
distance must not exceed:
(a) TORA
(b) 1.15 x TODA
(c) 1.3 x ASDA
• If the runway is not a dry paved surface, then the following
factor must be applied:
(a) Wet paved surface: x 1.0
(b) Dry grass surface: x 1.2
(c) Wet grass surface: x 1.3
• Increase take-off distance by 5% per 1% of upslope (do not
make any downslope corrections).
Take-off Speeds
The Take-off and Obstacle Clearance graph is based on the
following speeds:
MASS (kg) TAKE-OFF SPEED (kt)
ROTATION 50ft
2,800
2,600
2,400
2,200
2,000
81
79
78
76
74
89
87
84
81
78
-
Copyright © ASPEQ Limited 2011 7 of 20
DIAGRAM 32.12
Take-off Performance (LTA)
-50
0+
50
2,8
00
2,6
00
2,4
00
2,0
00
0-1
0+
10
+30
+20
250
500
750
1,0
00
ISA
10,0
00
8,0
00
6,0
00
4,0
00
2,0
00
SL
PR
ES
SU
RE
ALT
ITU
DE
(ft
)
MA
SS
(kg
)W
IND
CO
MP
ON
EN
T (
kt)
REFERENCE LINE
REFERENCE LINE
REFERENCE LINE
TAKE-OFF DISTANCE (m)
Exa
mp
le
Te
mp
era
ture
= 1
4˚C
Altitu
de
= 3
,500
ft
Ta
ke
-off
ma
ss =
2,6
70
kg
Win
d c
om
pon
en
t =
+1
7kt
Ta
ke
-off
gro
un
d r
oll
= 4
20m
Ta
ke
-off
dis
tance
= 5
70m
TE
MP
ER
AT
UR
E (̊
C)
2,2
00
0
CL
EA
RA
NC
E H
EIG
HT
(ft
)
50
-
8 of 20 Copyright © ASPEQ Limited 2011
DIAGRAM 32.14
Cruise Power Settings (LTA)
The following table provides cruise power settings, together
with resultant fuel flow and airspeed for a light twin-engine
aeroplane.
75% Power – High Speed Cruise
Pressure
altitude (feet)
IOAT
(˚C)
Manifold pressure
(“ Hg)
Fuel Flow
(kg/hr)
Airspeed
IAS (kt) TAS (kt)
0 17 33.0 79 159 159
2,000 13 32.7 80 158 163
4,000 9 32.4 81 158 167
6,000 5 32.1 81 158 173
8,000 1 31.7 80 156 176
10,000 -3 31.5 79 154 179
12,000 -7 31.3 78 151 182
14,000 -11 31.1 77 148 184
16,000 -3 - - - -
18,000 -7 - - - -
20,000 -11 - - - -
60% Power – Economy Cruise
Pressure
altitude (feet)
IOAT
(˚C)
Manifold pressure
(“ Hg)
Fuel Flow
(kg/hr)
Airspeed
IAS (kt) TAS (kt)
0 17 28.1 59 149 149
2,000 13 27.7 60 148 152
4,000 9 27.3 61 147 156
6,000 5 27.0 61 146 162
8,000 1 26.6 60 145 165
10,000 -3 25.4 59 144 168
12,000 -7 25.1 58 143 171
14,000 -11 24.7 57 141 173
16,000 -3 24.2 56 139 175
18,000 -7 - - - -
20,000 -11 - - - -
The following corrections need to be made to the above data for
temperature variations:
• reduce/increase fuel flow by 3kg/hr per 10˚C above/below
ISA.
• reduce/increase IAS and TAS by 4kt per 10˚C above/below
ISA.
-
Copyright © ASPEQ Limited 2011 9 of 20
45% Power – Long Range Cruise
Pressure
altitude (feet)
IOAT
(˚C)
Manifold pressure
(“ Hg)
Fuel Flow
(kg/hr)
Airspeed
IAS (kt) TAS (kt)
0 17 24.1 54 125 125
2,000 13 23.7 54 124 128
4,000 9 23.3 55 123 131
6,000 5 23.0 55 122 134
8,000 1 22.7 54 121 137
10,000 -3 22.5 53 120 141
12,000 -7 22.2 52 119 144
14,000 -11 21.9 51 118 147
16,000 -15 21.6 50 118 151
18,000 - 19 21.3 48 117 155
20,000 - 23 20.9 47 117 159
Cruise Power Setting Adjustments
• reduce/increase fuel flow by 2g/hr per 10˚C above/below
ISA.
• reduce/increase IAS and TAS by 3kt per 10˚C above/below
ISA.
Endurance and Range (LTA)
18,000
16,000
14,000
12,000
10,000
8,000
6,000
4,000
2,000
SL
6:00 7:00
ENDURANCE (hrs)
RANGE (nm)
600 700 800 900
75%
60%
45% Power
4:00 5:00
75%
60%
Data includes start,
taxi, take-off and 45
minutes reserve
at 45% power.
Example
For 60% cruise
at 8,500 feet:
Endurance = 5:25
Range = 728nm
45% Power
-
10 of 20 Copyright © ASPEQ Limited 2011
DIAGRAM 32.16
Landing Performance – LTA
-50
0+
50
2,8
00
2,6
00
2,4
00
2,0
00
0-1
0+
10
+30
+20
050
250
500
750
1,0
00
ISA
10
,00
0
PR
ES
SU
RE
ALT
ITU
DE
(ft
)
MA
SS
(kg
)W
IND
CO
MP
ON
EN
T (
kt)
OB
ST
AC
LE
HE
IGH
T (
ft)
REFERENCE LINE
REFERENCE LINE
REFERENCE LINE
DISTANCE (m)
Exa
mp
le
Te
mp
era
ture
= +
8˚C
Altitu
de
= 5
,000
ft
Mass =
2,3
30
kg
Win
d c
om
pon
en
t =
-7
kt
Lan
din
g r
oll
= 3
20m
Lan
din
g d
ista
nce
(o
ve
r 5
0ft
obsta
cle
) =
480m
TE
MP
ER
AT
UR
E (̊
C)
8,0
00
6,0
00
4,0
00
2,0
00
SL
2,2
00
1,2
50
-
Copyright © ASPEQ Limited 2011 11 of 20
DIAGRAM 32.18
Performance Data – Medium Range Jet (MRJ) General Information
This performance data is for a generic medium range jet transport
aeroplane which is configured as follows:
Monoplane, Two high-bypass turbo-fan engines, Retractable
undercarriage, Performance Class A. Structural Limits Maximum Ramp
Mass 63,030kg Maximum Take-off Mass 62,800kg Maximum Landing Mass
54,900kg Maximum Zero Fuel Mass 51,300kg Fuel Data Maximum Fuel
Load 13,200litres Taxi fuel 1,200kg/hr APU fuel consumption
115kg/hr Fuel density 0.80kg/lt (unless otherwise stated)
Operational Cost Index 25 (“CI 25”, unless otherwise stated)
Air Conditioning Increase fuel consumption by 1% when operating
packs at “HI FLOW” Icing Increase fuel consumption as follows:
Engine anti-ice only 70kg/hr Engine and wing anti-ice 180kg/hr
-
12 of 20 Copyright © ASPEQ Limited 2011
DIAGRAM 32.20
Field Length Brake Release Mass (MRJ)
4,000
SL
OP
E (
%)
0-2
+2
-20
030
20
10
WIN
D C
OM
PO
NE
NT
(kt)
15
5
FL
AP
PO
SIT
ION
AVAILABLE FIELD LENGTH (m)
FIE
LD
LE
NG
TH
BR
AK
E R
EL
EA
SE
MA
SS
(1,0
00 k
g)
35
40
45
50
55
60
63
3,000 2,000 1,000
-25 0 +25 +50
AMBIENT TEMPERATURE (˚C)
REFERENCE LINE
REFERENCE LINE
REFERENCE LINE
RE
FE
RE
NC
E L
INE
PRESSURE
ALTITUDE
(1,000 ft)
10,000
8,000
6,000
4,000
2,000
SL
Example
Available field length = 2,100m
Slope = -0.5%
Wind component = +12kt
Flap position = 5
Temperature = 18˚C
Altitude = 1,500ft
Mass = 60,000kg
Field Length Brake Release Mass Adjustments
• Increase mass by 550kg if air-conditioning packs are OFF for
take-off.
• Decrease mass by 350kg if engine anti-icing is ON for
take-off.
-
Copyright © ASPEQ Limited 2011 13 of 20
DIAGRAM 32.22
Maximum Brake Energy Speed (MRJ) Decrease brake release mass
(BRM) by 300kg per knot that V1 exceeds VMBE, as per the following
graph. Then
determine normal V1, VR and V2 for lower BRM.
-50 +500 150 175 200
AMBIENT TEMPERATURE (˚C)BRAKE ENERGY LIMIT
SPEED VMBE (kt IAS)
PRESSURE
ALTITUDE (ft)
2,000
SL
4,000
8,000
-1,000
6,000
Example
Take-off from runway
at 6,000ft and 25˚C
Mass = 60,000kg
VMBE = 168kt IAS
MASS
(1,000 kg)50
55
60
63
Brake Energy Speed Adjustments
• Increase VMBE by 1kt per 3kt of headwind component.
• Increase VMBE by 2kt per 1kt of tailwind component.
• Increase VMBE by 2kt per 1% upslope.
• Decrease VMBE by 5kt per 1% downslope.
-
14 of 20 Copyright © ASPEQ Limited 2011
DIAGRAM 32.24
Take-off Climb Limit (MRJ)
65
60
55
50
45
40
35
CL
IMB
LIM
IT B
RA
KE
RE
LE
AS
E M
AS
S (
1,0
00kg
)
15 5
FLAP
POSITION
10 AND
BELOW
20
5
30
5
40
5
50
5AMBIENT TEMPERATURE (˚C)
RE
FE
RE
NC
E L
INE
SL
1,000
2,000
4,000
3,000
5,000
6,000
8,000
7,000
PRESSURE
ALTITUDE (ft)
Example
Temperature = +25˚C
Altitude = 7,000ft
Flap = 15˚
Climb limit mass = 51,200kg
Climb Limit Brake Release Mass Adjustments
• Increase mass by 850kg if air-conditioning packs are OFF for
take-off.
• Decrease mass by 200kg if engine anti-icing is ON for
take-off.
-
Copyright © ASPEQ Limited 2011 15 of 20
DIAGRAM 32.26
Reduced Thrust Take-off – Assumed Temperature Method There may
occasions where the actual brake release mass is significantly
lower than all of the limiting take-
off masses, and a lower thrust setting may therefore be used to
safely complete the take-off. One method of
determining how much thrust reduction is available is to compare
the limiting take-off temperatures for the
actual brake release mass. The lowest of these limiting
temperatures may then be used as a basis for thrust
reduction.
Note that thrust reduction must not be used under the following
conditions:
• Icy or very slippery runways
• Contaminated runways
• When certain aeroplane systems e.g. anti-skid are
inoperative
To obtain the ‘Assumed Temperature’ thrust reduction value,
first determine the most limiting (i.e. the lowest)
maximum temperature for each of the following:
• Field limit graph
• Climb limit graph
• Obstacle clearance limit graph
Next determine the maximum assumed temperature from the
following table:
OAT (˚C) PRESSURE ALTITUDE (ft)
SL 1,000 2,000 3,000 4,000 5,000 6,000 7,000 8,000
50
45
40
69
67
65
68
66
64
68
66
64
69
67
64
70
67
64
67
64
68
64
70
66
68
35
30
25
63
61
61
62
60
59
62
60
58
62
59
57
61
59
56
61
59
56
62
59
56
63
60
57
64
61
58
20
15 and
below
61
61
59
59
58
58
57
57
55
55
53
53
54
53
54
52
55
52
Use the assumed temperature thrust (N1) from the table
below:
ASSUMED
TEMP. (˚C)
PRESSURE ALTITUDE (ft)
SL 1,000 2,000 3,000 4,000 5,000 6,000 7,000 8,000
75
70
65
60
85.4
87.6
89.7
91.8
85.4
87.6
89.7
91.8
87.4
89.2
91.3
87.6
89.2
90.8
89.2
90.7
89.3
90.7
89.5
90.8
89.9
91.1
90.4
91.4
55
50
45
40
93.8
94.3
94.7
95.2
93.8
94.3
94.7
95.2
92.7
93.2
94.6
95.1
92.4
93.9
94.6
95.0
92.1
93.6
94.6
95.1
92.1
93.4
94.7
95.1
92.0
93.2
94.4
95.2
92.1
93.2
94.2
95.1
92.3
93.2
94.0
94.9
35
30
25
20
95.6
96.1
95.6
96.6
95.6
96.0
96.5
95.5
96.0
96.5
95.7
96.3
96.7
97.1
95.7
96.2
96.6
97.1
95.7
96.1
96.6
97.1
95.6
96.0
96.5
97.0
95.5
96.0
96.4
96.9
-
16 of 20 Copyright © ASPEQ Limited 2011
DIAGRAM 32.28
Climb Time, Fuel, Distance and TAS Table units are time in
minutes, fuel used in kilograms, still air distance in nautical
miles and average TAS in knots.
PRESSURE ALTITUDE
(ft)
BRAKE RELEASE MASS (kg)
40,000 45,000 50,000 55,000 60,000 65,000
37,000 12
68
1,000
385
15
82
1,140
386
17
97
1,325
388
20
119
1,550
391
26
175
1,900
396 - -
35,000 11
60
950
381
13
71
1,075
382
15
84
1,225
383
17
97
1,375
385
21
121
1,650
388
27
154
2,000
392
33,000 10
54
900
376
12
64
1,025
377
14
75
1,150
378
15
84
1,310
380
18
103
1,550
381
22
124
1,775
384
31,000 9
49
850
371
11
57
975
371
12
66
1,000
372
14
77
1,260
374
16
89
1,400
375
19
106
1,625
377
29,000 9
43
800
364
10
51
915
364
12
58
1,025
365
13
67
1,175
366
14
77
1,300
367
17
90
1,500
368
27,000 8
37
750
56
9
44
825
356
11
50
950
356
12
56
1,075
357
13
65
1,200
358
15
75
1,375
358
25,000 7
32
700
348
8
37
775
348
9
43
875
349
10
49
975
349
11
55
1,100
350
13
64
1,225
350
20,000 5
22
550
332
6
25
625
332
7
29
725
332
8
32
785
332
9
37
900
332
10
41
975
332
15,000 4
14
450
317
5
16
515
317
5
18
575
317
6
21
640
317
6
23
700
317
7
26
775
317
10,000 3
8
350
304
3
9
400
304
4
11
425
304
4
12
490
305
4
13
550
305
5
15
575
305
5,000 2
4
250
295
3
5
300
295
3
5
325
295
3
6
350
295
3
6
400
295
3
7
425
295
Enroute Climb Information Adjustments
• No time correction need be considered for temperature
variations.
• Increase/reduce distance by 1nm per 2˚C above/below ISA.
• Add/subtract 3% of distance per 10 knots of
tailwind/headwind.
• Increase/reduce fuel used by 1% per 2˚C above/below ISA.
• Increase/reduce TAS by 1% per 5˚C above/below ISA.
-
Copyright © ASPEQ Limited 2011 17 of 20
DIAGRAM 32.30
Optimum Cruise Altitude
38,000
36,000
34,000
32,000
30,000
28,000
45,000 60,00055,00050,000 65,000
MAXIMUM OPERATING ALTITUDE
65,00060,00055,00050,00045,000
CRUISE MASS (1,000kg)
BRAKE RELEASE MASS (1,000kg)
ExampleCruise mass = 62,000kgOptimum altitude = 31,750 feet
ALTITUDE (ft)
Off-Optimum Altitude
If unable to operate at the optimum cruise altitude as per the
above the graph and the Optimum Altitude Trip Time and
Fuel graph, then the following penalty should be applied:
OFF-OPTIMUM
ALTITUDE
FUEL MILAGE PENALTY (%)
LRC CI = 25
2,000ft above 1 1
Optimum 0 0
2,000ft below 1 3
4,000ft below 4 5
8,000ft below 10 13
10,000ft below 15 22
-
18 of 20 Copyright © ASPEQ Limited 2011
DIAGRAM 32.32
Cruise Fuel Flow and Speed The following table provides cruise
fuel flow (in kg/hr) for a given cruising level and aeroplane
weight (at 300kt TAS for
10,000ft and Cost Index 25 for all other altitudes).
TOTAL
MASS (kg)
PRESSURE ALTITUDE (ft)
10,000 20,000 27,000 29,000 31,000 33,000 35,000 37,000
63,000 2,050
300
2,440
0.71
1,970
0.73
1,850
0.74
1,800
0.74
1,760
0.74
- -
60,000 2,000
300
2,380
0.71
1,910
0.73
1,790
0.74
1,700
0.74
1,650
0.74
1,650
0.74
-
58,000 1,955
300
2,320
0.71
1,850
0.73
1,730
0.74
1,640
0.74
1,580
0.74
1,560
0.74
1,650
0.74
56,000 1,910
300
2,260
0.70
1,800
0.73
1,670
0.74
1,580
0.74
1,510
0.74
1,480
0.74
1,520
0.74
54,000 1,860
300
2,200
0.70
1,760
0.72
1,620
0.74
1,520
0.74
1,440
0.74
1,390
0.74
1,400
0.74
52,000 1,830
300
2,170
0.69
1,720
0.72
1,580
0.73
1,470
0.74
1,380
0.74
1,320
0.74
1,320
0.74
50,000 1,800
300
2,140
0.69
1,680
0.72
1,540
0.73
1,420
0.74
1,320
0.74
1,260
0.74
1,250
0.74
48,000 1,770
300
2,120
0.68
1,640
0.72
1,500
0.73
1,370
0.73
1,270
0.74
1,200
0.74
1,170
0.74
46,000 1,750
300
2,100
0.67
1,610
0.71
1,460
0.72
1,330
0.73
1,220
0.74
1,150
0.74
1,110
0.74
44,000 1,730
300
2,080
0.65
1,580
0.71
1,430
0.72
1,290
0.73
1,180
0.73
1,100
0.74
1,050
0.74
42,000 1,710
300
2,060
0.64
1,560
0.71
1,400
0.72
1,250
0.73
1,140
0.73
1,050
0.74
990
0.74
40,000 1,680
300
2,040
0.63
1,540
0.70
1,370
0.72
1,230
0.72
1,100
0.73
1,000
0.74
930
0.74
38,000 1,650
300
2,020
0.62
1,520
0.73
1,340
0.72
1,210
0.72
1,060
0.73
950
0.73
880
0.74
36,000 1,630
300
2,000
0.61
1,500
0.73
1,310
0.72
1,190
0.72
1,020
0.72
900
0.73
830
0.74
Fuel and Speed Adjustments
• Increase/reduce fuel used by 0.5% per 10˚C above/below
ISA.
• Increase/reduce Mach number by 2% per 10˚C above/below
ISA.
• Add 15kg fuel used per 1,000 feet of cruise climb.
-
Copyright © ASPEQ Limited 2011 19 of 20
DIAGRAM 32.34
Descent Time, Fuel and Distance Descent profile = M0.74/288kt
IAS to 10,000 feet; then 250kt IAS.
PRESSURE
ALTITUDE
(ft)
TIME
(min)
FUEL
(kg)
DISTANCE (nm)
LANDING WEIGHT (kg)
35,000 40,000 45,000 50,000 55,000
37,000
35,000
33,000
31,000
23
22
21
20
295
290
285
280
98
94
89
83
103
99
94
88
109
105
99
93
112
108
101
95
114
110
103
97
29,000
27,000
25,000
23,000
19
18
17
16
275
270
260
255
78
73
68
63
83
77
72
66
87
81
75
69
89
83
77
71
91
85
79
72
21,000
19,000
17,000
15,000
15
14
13
12
245
235
225
215
58
53
48
43
61
56
50
45
64
58
52
46
65
59
53
47
66
60
54
48
10,000
5,000
9
6
185
140
30
18
31
18
32
18
33
18
33
18
Descent Time and Distance Adjustments
• No temperature adjustment need be considered.
• Add/subtract 3% of distance per 10 knots of
tailwind/headwind.
• For overweight landings, use the 55,000kg data.
• For CI = 0 descent add 1.5nm per thousand feet above
10,000feet.
• For engine anti-ice during descent add 50kg of fuel.
• Above information is for a ‘straight-in’ approach - add 400kg
and 10 minutes for a full instrument approach.
-
20 of 20 Copyright © ASPEQ Limited 2011
DIAGRAM 32.36
Landing Field Length (MRJ)
1,000 1,500 2,000 2,500 3,000
AVAILABLE FIELD LENGTH (m)
-20
0
+20
+40
DRY
WET
40
30
40
45
50
55
60
63
0 2 4 860 2 4 6 8
PRESSURE
ALTITUDE (1,000ft)
ANTI-SKID
OPERATIVE
REFERENCE LINE
REFERENCE LINE
REFERENCE LINE
15
WIN
D C
OM
PO
NE
NT
(kt)
SU
RF
AC
E
CO
ND
ITIO
N
FL
AP
SE
TT
ING
FIE
LD
LE
NG
TH
LIM
IT M
AS
S (
kg
)
Example
Field Length = 1,860m
Wind = +20kt
Surface = wet
Flap = 30˚
Anti-skid = operative
Altitude = 2,500ft
Limit mass = 60,500kg
1,000 1,500 2,000 2,500 3,000
AVAILABLE FIELD LENGTH (m)
-20
0
+20
+40
DRY
WET
40
30
40
45
50
55
60
63
0 2 4 860 2 4 6 8
PRESSURE
ALTITUDE (1,000ft)
ANTI-SKID
OPERATIVE
REFERENCE LINE
REFERENCE LINE
REFERENCE LINE
15
WIN
D C
OM
PO
NE
NT
(kt)
SU
RF
AC
E
CO
ND
ITIO
N
FL
AP
SE
TT
ING
FIE
LD
LE
NG
TH
LIM
IT M
AS
S (
kg
)
Example
Field Length = 1,860m
Wind = +20kt
Surface = wet
Flap = 30˚
Anti-skid = operative
Altitude = 2,500ft
Limit mass = 60,500kg
PRESSURE ALTITUDE
(1,000ft)
ANTI-SKID INOP
![00 FOA G10 WB - 1st pages [1 Sep 2011] · 2016. 1. 5. · Focus Account 10 WB cov-REV2.indd 1 2011/10/06 9:35 AM. ii Focus Accounting Grade 10 Workbook Maskew Miller Longman (Pty)](https://img.pdfslide.net/doc/110x75/61496a81080bfa6260149890/00-foa-g10-wb-1st-pages-1-sep-2011-2016-1-5-focus-account-10-wb-cov-rev2indd.jpg)